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Multi-disciplinary conceptual design of future jet engine systems

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Multi-disciplinary conceptual design of future jet engine systems ( multi-disciplinary-conceptual-design-future-jet-engine-syste )

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Konstantinos G. Kyprianidis Low pressure system component advancements Figure 5.4: Future ultra high bypass ratio engine designed using year 2020 VITAL low pressure spool objective technology (upper half) and year 2000 entry into service technology (lower half). in a nine stage turbine, whereas the year 2020 LPT uses a value of 5.2. It is also demonstrated how improved aerodynamics of the intermediate and high pressure compressor components will contribute to a lighter and more compact engine. Finally, the use of an MMC shaft can make a future engine more compact and more space made available for the high pressure turbine discs. The Ultra-High Bypass Ratio (UHBR) engine design illustrated in the upper half of Fig. 5.4 may be considered as an optimal one assuming all 2020 technology targets are met. On the other hand, the UHBR engine design illustrated in the bottom half of the figure may be considered as uncompetitive one since important size, weight and SFC penalties (for year 2000 entry into service technology) would shift the optimal specific thrust and bypass ratio levels to higher and lower values respec- tively. 5.4 Conclusion In this chapter the TERA2020 tool was used to establish a number of sensi- tivity factors relating traditionally used component design parameters to en- gine/aircraft performance parameters. The resulting sensitivity factors allow a straightforward evaluation of the system level impact of component technology research progress. In particular, results were provided for the three VITAL engine configurations, with respect to aerodynamics, weights and noise, for two different 127

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